Wind tunnel investigation of dynamic stall of a NACA 0018 Airfoil oscillating in Pitch

This report presents aerodynamic data on an NACA 0018 airfoil oscillating in pitch in the N AE 2m X 3m Low Speed Tunnel. The purpose of the test was to simulate the dynamic aerodynamic behaviour of a Vertical Axis Wind Turbine blade section at the equatorial plane under the dynamic stall conditions which may occur at low ratios of tip speed to...

The vortex wake and aerodynamic load distribution of slender retangular plates; the effects of a 20-degree bend at mid-chord

Observations of the vortex wake of a lifting fuselage similar to those on rear-loading transport aircraft

The vortex wake of a lifting fuselage, similar to those employed on rear-loading transport aircraft has been investigated using the N.A.E. Flow Visualization Water Tunnel. Both quantitative and qualitative information has been derived from photographs. For negative incidences, the flow adjacent to the body and in the wake was composed of two...

Calculation of the equilibrium locations of a vortex pair behind a circular cylinder with a source or sink placed at the rear stagnation point

The equilibrium positions of a vortex pair of specified strength behind a circular cylinder in steady, potential flow have been calculated with a souree or sink placed at the rear stagnation point.

Observations on the flow near a lifting propeller

The flow around a 31/2-inch diameter, 3-bladed propeller with its axis of rotation normal to the free stream direction bas been examined in tbe 10-inch x 13-inch N.A.E. flow visualization water tunnel. Both qualitative and quantitative information have been derived from photographs. At high advance ratios, the water tunnel observations showed...

Water tunnel experiments on a zap-flapped suction aerofoil

Suction was used to control the circulation about a two-dimensional aerofoil with a Zap flap; the suction served to eliminate the turbulent wake behind the flap and provided a substantial increase in lift. Flow photographs were taken from which force data were inferred. The test facility was the N.A.E. flow visualization water tunnel.

Wind tunnel and static thrust measurements on a four-blade constant chord propeller

Experiments have been conducted in order to evaluate the cruising and static performance of a high solidity model propeller. The results of the investigation revealed that the propeller was not highly erficient in the cruise (ŋ = 0 .72 ) when compared with current full-scale designs. Static thrust data indicated high performance at small blade...